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2023-16-04 PIAGGIO AVIATION S.P.A.: Amendment 39-22523; Docket No. FAA-2023-1712; Project Identifier MCAI-2023-00821-A.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective August 30, 2023.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD  applies to the following Piaggio Aviation S.p.A.  Model P-180
    airplanes, certificated in any category:

(1) Serial numbers (S/N) 1002,  1034 through 1234 inclusive,  3001 through
    3014 inclusive, 3016, and 3018; and

(2) S/N 1004 through 1033 inclusive if modified in accordance with Piaggio
    Service Bulletin 80-0142.

(d) SUBJECT

    Joint Aircraft System Component (JASC) Code: 5520, Elevator Structure.

(e) UNSAFE CONDITION

    This AD was prompted by a report of corrosion-induced cracking on  the
    horizontal  tail trim  actuator (HTTA)  fitting assembly.  The FAA  is
    issuing this  AD to  address structural  failure of  the HTTA  fitting
    assembly. The unsafe condition, if not addressed, could result in loss
    of control of the airplane.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) DEFINITIONS

(1) For purposes of this AD,  "light corrosion" is corrosion that does not
    exceed a depth of 0.15 millimeter  (mm)  and  does not extend beyond 1
    square inch (645.2 square mm).

(2) For purposes of this AD,  a "new part" is a part with zero hours time-
    in-service (TIS).

(h) INSPECTION

    Within the compliance time for your airplane listed in Table 1 to par-
    agraph (h) of this AD,  do a high frequency eddy current inspection of
    HTTA fitting assembly part number  (P/N) 80-363283-401  for  corrosion
    and cracking  in  accordance  with  Section 2.B.,  Part A,  Steps (11)
    through (14)  of the Accomplishment Instructions  in Piaggio Aerospace
    Service Bulletin 80-0492, Revision 3, dated June 12, 2023.
    ______________________________________________________________________
        TABLE 1 TO PARAGRAPH (H)  INITIAL INSPECTION COMPLIANCE TIME     
    ______________________________________________________________________
              AIRPLANES                             COMPLIANCE TIME
    ______________________________________________________________________
    Airplanes that have accumulated           Within 140 hours TIS or 8
    less than 3,000 hours TIS and             months after the effective
    less than 10 years since the date         date of this AD, whichever
    of issuance of the original air-          occurs first.
    worthiness certificate or original
    export certificate of airworthiness

    All other airplanes                       Within 30 hours TIS or 60
                                              days after the effective
                                              date of this AD, whichever
                                              occurs first.
    ______________________________________________________________________

(i) CORRECTIVE ACTIONS

    Based on  the result  of the  inspection required  by paragraph (h) of
    this AD,  do the  applicable corrective  action within  the applicable
    compliance time specified in Table 2 to paragraph (i) of this AD.
    ______________________________________________________________________
      TABLE 2 TO PARAGRAPH (I)  CORRECTIVE ACTIONS AND COMPLIANCE TIME   
    ______________________________________________________________________
        FINDING           COMPLIANCE TIME          CORRECTIVE ACTION
    ______________________________________________________________________
    No corrosion          Not applicable       Repeat inspection in
    and no cracking                            paragraph (h) of this AD at
                                               intervals not to exceed 660
                                               hours TIS or 26 months,
                                               whichever occurs first.

    Light corrosion       Before further       Repair light corrosion and
    and no cracking       flight               repeat inspection in
                                               paragraph (h) of this AD at
                                               intervals not to exceed 660
                                               hours TIS or 26 months,
                                               whichever occurs first.

    Corrosion exceeding   Before further       Replace the HTTA fitting
    light corrosion or    flight               assembly with a new part
    cracking on any part                       in accordance with Piaggio
    of the HTTA fitting                        Aerospace Temporary
    assembly                                   Revision TR-031 to
                                               Chapter 51-70-70, dated
                                               May 29, 2023, to the
                                               Piaggio P.180 Structural
                                               Repair Manual.
    ______________________________________________________________________

(j) TERMINATING ACTION

    Replacing the HTTA fitting assembly with a new part in accordance with
    Piaggio Aerospace Temporary Revision TR-031 to Chapter 51-70-70, dated
    May  29,  2023,  to   the  Piaggio  P.180  Structural   Repair  Manual
    constitutes terminating action for the repetitive inspections required
    by paragraph (i) of this AD for that airplane.

(k) CREDIT FOR PREVIOUS ACTION

    You may take credit for  the initial inspection required by  paragraph
    (h) of  this AD  if you  performed the  initial inspection  before the
    effective date of this AD using Piaggio Aerospace Service Bulletin  80
    -0492, Revision 2, dated May 15, 2023.

(l) REPORTING REQUIREMENT

    Report to the manufacturer the results of each inspection required  by
    paragraphs (h)  and (i)  of this  AD within  the applicable compliance
    time  specified  in paragraph  (l)(1)  or (2)  of  this AD  using  the
    Confirmation Slip  attached  to  Piaggio Aerospace Service Bulletin 80
    -0492, Revision 3, dated June 12, 2023.

(1) If the inspection was done on  or after the effective date of this AD:
    Submit the report within 10 days after the inspection.

(2) If the inspection was done  before the effective date of this AD: Sub-
    mit the report within 10 days after the effective date of this AD.

(m) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

    The Manager, International Validation Branch,  FAA,  has the authority
    to approve AMOCs for this AD, if requested using the procedures  found
    in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to
    your principal inspector or local Flight Standards District Office, as
    appropriate. If  sending information  directly to  the manager  of the
    International Validation Branch, mail it to the address identified  in
    paragraph (n)(2) of this  AD or email to:  9-AVS-AIR-730-AMOC@faa.gov.
    If mailing information, also submit information by email. Before using
    any approved  AMOC, notify  your appropriate  principal inspector,  or
    lacking  a  principal  inspector,  the  manager  of  the  local flight
    standards district office.

(n) ADDITIONAL INFORMATION

(1) Refer to European Union Aviation Safety Agency  (EASA) AD 2023-0122R1,
    dated July 5, 2023, for related information. This EASA AD may be found
    in the AD docket at regulations.gov under Docket No. FAA-2023-1712.

(2) For more information about this AD contact Mike Kiesov, Aviation Safe-
    ty Engineer, FAA,  1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
    phone: (816) 329-4144; email: mike.kiesov@faa.gov.

(3) Service information identified in this AD  that is not incorporated by
    reference is available at the addresses specified in paragraphs (o)(3)
    and (4) of this AD.

(o) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference of the service information  listed in this paragraph under 5
    U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable  to do the actions
    required by this AD, unless the AD specifies otherwise.

(i) Piaggio Aerospace Service Bulletin 80-0492, Revision 3, dated June 12,
    2023.

(ii) Piaggio Aerospace Temporary Revision TR-031 to Chapter 51-70-70 dated
     May 29, 2023, to the Piaggio P.180 Structural Repair Manual.

(3) For service information  identified in this AD,  contact  Piaggio Aero
    Industries S.p.A.,  P180  Customer  Support,  via  Pionieri e Aviatori
    d'Italia,  snc-16154 Genoa,  Italy;  phone: +39 331 679 74 93;  email:
    technicalsupport@piaggioaerospace.it.

(4) You may view this service information at the FAA,  Airworthiness Prod-
    ucts Section,  Operational Safety Branch,  901 Locust, Kansas City, MO
    64106. For information on the availability of this material at the FAA
    call (817) 222-5110.

(5) You may view  this service information  that is incorporated by refer-
    ence at the National Archives and Records Administration  (NARA).  For
    information on the availability of this material  at NARA,  email: fr.
    inspection@nara.gov,  or go to: www.archives.gov/federal-register/cfr/
    ibr-locations.html.

Issued on August 8, 2023.  Victor Wicklund,  Deputy Director, Compliance &
Airworthiness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Mike Kiesov,  Aviation  Safety  Engineer,
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (816) 329-
4144; email: mike.kiesov@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39


[Docket No. FAA-2023-1712; Project Identifier MCAI-2023-00821-A;
Amendment 39-22523; AD 2023-16-04]
RIN 2120-AA64

Airworthiness Directives; Piaggio Aviation S.p.A. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Piaggio Aviation S.p.A. (Piaggio) Model P-180 airplanes. This
AD was prompted by a report of corrosion-induced cracking on the
horizontal tail trim actuator (HTTA) fitting assembly. This AD requires
repetitively inspecting the HTTA fitting assembly for corrosion and
cracking until the HTTA fitting assembly is replaced with a new part.
The FAA is issuing this AD to address the unsafe condition on these
products.

DATES: This AD is effective August 30, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 30,
2023.
The FAA must receive comments on this AD by September 29, 2023.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-1712; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this final rule, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
For service information identified in this final rule,
contact Piaggio Aero Industries S.p.A., P180 Customer Support, via
Pionieri e Aviatori d'Italia, snc-16154 Genoa, Italy; phone: +39 331
679 74 93; email: technicalsupport@piaggioaerospace.it.
You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 901 Locust,
Kansas City, MO 64106. For information on the availability of this
material at the FAA, call (817) 222-5110. It is also available at
regulations.gov under Docket No. FAA-2023-1712.

FOR FURTHER INFORMATION CONTACT: Mike Kiesov, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (816)
329-4144; email: mike.kiesov@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments to an address listed under
ADDRESSES. Include ``Docket No. FAA-2023-1712; Project Identifier MCAI-
2023-00821-A'' at the beginning of your comments. The most helpful
comments reference a specific portion of the final rule, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this final rule because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this final rule.

Confidential Business Information

CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this AD contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this AD, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this AD. Submissions containing CBI should be sent to Mike
Kiesov, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590. Any commentary that the FAA receives which is not
specifically designated as CBI will be placed in the public docket for
this rulemaking.

Background

The European Union Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Union, has issued
EASA AD 2023-0122R1, dated July 5, 2023
(referred to after this as the MCAI), to correct an unsafe condition on
certain serial-numbered Piaggio Model P.180 airplanes. The MCAI states
an occurrence was reported where, during scheduled maintenance, stress
corrosion-induced cracking was found on the HTTA fitting assembly. The
MCAI states that this type of corrosion can be found on older
airplanes, based and operated for an extended period of time near the
seaside, exposed to a salty environment, or parked outside in an
environment of high humidity or frequent heavy precipitation.
To address the unsafe condition, the MCAI requires doing a high
frequency eddy current inspection (HFEC) of the HTTA fitting assembly
for corrosion and cracking and, depending on the findings, repeating
the inspection and repairing any light corrosion, or replacing the HTTA
fitting assembly with a new part. The MCAI states that replacing the
HTTA fitting assembly terminates the repetitive inspections.
This condition, if not addressed, could result in structural
failure of the HTTA fitting assembly and loss of control of the
airplane. You may examine the MCAI in the AD docket at regulations.gov
under Docket No. FAA-2023-1712.

Related Service Information Under 1 CFR Part 51

The FAA reviewed Piaggio Aerospace Service Bulletin 80-0492,
Revision 3, dated June 12, 2023. This service information specifies
procedures for doing an HFEC inspection of the HTTA fitting assembly
for corrosion and taking corrective actions. The corrective actions
include repeating the HFEC inspection, repairing light corrosion, and
replacing the HTTA fitting assembly with a new part.
The FAA also reviewed Piaggio Aerospace Temporary Revision TR-031
to Chapter 51-70-70, dated May 29, 2023, to the Piaggio P.180
Structural Repair Manual. This service information specifies procedures
for replacing the HTTA fitting assembly.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in ADDRESSES section.

FAA's Determination

These products have been approved by the aviation authority of
another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with this State of Design
Authority, it has notified the FAA of the unsafe condition described in
the MCAI and service information referenced above. The FAA is issuing
this AD after determining that the unsafe condition described
previously is likely to exist or develop on other products of the same
type design.

AD Requirements

This AD requires accomplishing the actions specified in the service
information already described, except as discussed under ``Differences
Between this AD and the MCAI.''

Differences Between This AD and the MCAI

The MCAI allows airplanes with corrosion or cracking in certain
areas of the HTTA fitting assembly to continue flights and be repaired
within 150 hours time-in-service or 7 months, whichever occurs first.
This AD requires that airplanes with corrosion exceeding light
corrosion or with cracking on any part of the HTTA fitting assembly be
repaired before further flight.

Justification for Immediate Adoption and Determination of the Effective
Date


Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and
comment procedures for rules when the agency, for ``good cause,'' finds
that those procedures are ``impracticable, unnecessary, or contrary to
the public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies forgoing notice and comment prior to adoption of this rule
because corrosion on the HTTA fitting assembly could lead to cracking
that, if not addressed, could result in structural failure of the HTTA
fitting assembly and loss of control of the airplane. For certain
airplanes, the initial HFEC inspection must be accomplished within 30
hours time-in-service or 60 calendar days after the effective date of
this AD, whichever occurs first. This compliance time is shorter than
the time necessary for the public to comment and for publication of the
final rule. Accordingly, notice and opportunity for prior public
comment are impracticable and contrary to the public interest pursuant
to 5 U.S.C. 553(b)(3)(B).
In addition, the FAA finds that good cause exists pursuant to 5
U.S.C. 553(d) for making this amendment effective in less than 30 days,
for the same reasons the FAA found good cause to forgo notice and
comment.

Regulatory Flexibility Act

The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without prior notice and
comment, RFA analysis is not required.

Costs of Compliance

The FAA estimates that this AD affects 103 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:

Estimated Costs

Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Initially inspect HTTA fitting assembly 55 work-hours x $85 per hour = $4,675
$0
$4,675
$481,525
Report results 1 work-hour x $85 per hour = $85
0
85
8,755

The FAA estimates the following costs to do any necessary
corrective action that would be required based on the results of any
inspection. The agency has no way of determining the number of aircraft
that might need these actions:

On-Condition Costs

Action
Labor cost
Parts cost
Cost per product
Repetitively inspect HTTA fitting assembly 55 work-hours x $85 per hour = $4,675
0
$4,675 per inspection cycle
Report results 1 work-hour x $85 per 0 hour = $85
0
$85
Repair light corrosion 1 work-hour x $85 per 0 hour = $85
0
$85 per inspection cycle
Replace HTTA fitting assembly 13 work-hours x $85 per hour = $1,105
4,750
$5,855

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to take
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden, to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings

This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866, and
(2) Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Amendment


Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive: